CN103913099A - Integral hollow composite material firing box cover - Google Patents
Integral hollow composite material firing box cover Download PDFInfo
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- CN103913099A CN103913099A CN201410090565.3A CN201410090565A CN103913099A CN 103913099 A CN103913099 A CN 103913099A CN 201410090565 A CN201410090565 A CN 201410090565A CN 103913099 A CN103913099 A CN 103913099A
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Abstract
The invention relates to an integral hollow composite material firing box cover, and belongs to the technical field of missile firing. The integral hollow composite material firing box cover comprises a framework (1) and an ejection body (3), wherein the joint of the framework (1) and the ejection body (3) is called separation region (2). The integral hollow composite material firing box cover is characterized in that the ejection body (3) is molded by curing a middle interlayer and glass fiber cloth layers on both sides through an epoxy resin adhesive serving as a substrate; a V-shaped chamfer angle is formed on both sides of the edge of the ejection body (3) respectively, thereby forming a double V-shaped chamfer region (6); the double V-shaped chamfer region (6) is glued with the edge of the framework (1) after being filled with an AB adhesive; the edge of the ejection body (3) and the edge of the framework (1) are attached with glass fiber cloth strips (5) on the inner side through the epoxy resin adhesive, and are sealed through an epoxy resin adhesive layer (7) on the outer side. The integral hollow composite material firing box cover has the advantages of simple structure, high bearing capacity, light structural weight and high stability.
Description
Technical field
The present invention relates to a kind of integral hollow composite material launching box cover, belong to MISSILE LAUNCHING technical field.
Background technology
The design of MISSILE LAUNCHING case lid is to affect guided missile to reflect fast one of key factor of ability.Therefore in the time of development missile storage firing box, the design of case lid is extremely important.Case lid is mainly to bear certain pressure reduction, and good seal performance can be opened rapidly in the time launching a guided missile.For meeting above-mentioned requirements, MISSILE LAUNCHING case lid used adopts mechanical cap, and blasting bolt open cap etc. (refers to US Pat.3970006,1976; US Pat.4333381,1982), but the shortcoming of the equal various degrees of these case lids, opening lid as machinery need to open by hydraulic system, and mechanism's complexity has not only increased the weight of firing box and wasted time, blast lid is opened and is reacted rapid compared with mechanical cap, but again shoot and keep in repair more complicated, and adopt priming system transport, storage difficulty.
For improving MISSILE LAUNCHING efficiency, meet the requirement that army fights fast, develop a kind of composite frangible membrane will case lid (referring to US Pat.4498368,1985) abroad.This kind of case lid can bear certain well-distributed pressure and under less concentrated force, just can make case lid to subscribe track fragmentation, is swift in response, and improved MISSILE LAUNCHING efficiency.But this kind of composite material launching box cover need destroy under the effect of guided missile end, case lid will inevitably produce certain adverse effect to the guided missile warhead of contact with it.Domestic a kind of integral impacting type composite canister cover (referring to CN1844839A, 2006), the gas shock film cover of utilizing the front engine of MISSILE LAUNCHING to produce, film cover is destroyed with desired trajectory entirety, can not have a negative impact to MISSILE LAUNCHING.But the woven fabric number of plies of this kind of film cover laying is more, and film cover is thicker, comparatively heavy when use, and Disengagement zone scope is larger, easily forms internal flaw, causes overall performance to decline, the more difficult control of quality stability.Therefore, have some limitations when the launching box cover practical application of this type.
Summary of the invention
The object of the present invention is to provide that a kind of simple in structure, bearing capacity is strong, the integral hollow composite material launching box cover of lightweight construction, good stability.
A kind of integral hollow composite material launching box cover of the present invention, comprising: framework (1) and the body of dishing out (3), and framework (1) and the body of dishing out (3) junction are called Disengagement zone (2); It is characterized in that:
The described body of dishing out (3) is by middle sandwich of layers, and the glass fibre layer of cloth of both sides is that matrix curing molding forms by epoxide-resin glue;
The described body of dishing out (3) both sides of edges respectively has a V-type chamfering, be called double V-shaped chamfered region (6), after the filling AB glue of double V-shaped chamfered region (6) with framework (1) edge-glued, and the body of dishing out (3) edge and framework (1) edge post glass fibre cloth (5) in inner side by epoxide-resin glue, seal with epoxy glue layer (7) in outside.
Operation principle of the present invention is: guided missile is stored in firing box before transmitting, now in case, has certain protective gas, and has certain interior pressure.Firing box is by the launching box cover sealing of upper and lower both sides, and before MISSILE LAUNCHING, case lid must bear certain interior pressure and possess good sealing property.Bear certain interior launching box cover of pressing and can produce distortion, case lid center (the body center of dishing out) is bending laterally, produces certain amount of deflection.From mechanics of materials knowledge, when the joist support of two fixed ends is subject to certain uniform load, the bending rigidity of beam is larger, and the deflection deformation of beam is less; Elastic modelling quantity and cross-sectional width one timing, the thickness of beam is larger, and bending rigidity is larger.Know by inference thus, the use of integral hollow fabric sandwich in body of dishing out has increased structural thickness, improve the bending rigidity of case lid, deflection deformation while having reduced case lid pressure-bearing, can meet the deformation requirements that launching box cover limits, than adopting pure composite material laminated board to reach this performance requirement, construction weight has alleviated 1 times.When guided missile igniting, produce high-speed fuel gas stream at its afterbody, and impact rapidly the launching box cover of the upper and lower both sides of firing box, this moment, case lid reaches the withstand voltage of setting, splits rapidly in Disengagement zone, and dish out body and framework apart are dished out, and guided missile is launched smoothly then.Adopt integral hollow fabric sandwich, the body structure weight that makes to dish out is lighter, dishes out and falls Shi Buhui to peripheral facilities generation destruction.Meanwhile, can regulate Disengagement zone to adjust the withstand voltage of launching box cover apart from the distance of framework and Disengagement zone thickness.
A kind of integral hollow composite material launching box cover of the present invention, is characterized in that: described sandwich of layers is integral hollow fabric sandwich or honeycomb interlayer or corrugated plating interlayer.
Use the beneficial effect that integral hollow fabric is sandwich of layers to be: simple in structure, bearing capacity strong, good stability, construction weight has alleviated 1 times, has improved the operation respond of missile unit; Adopt integral hollow fabric sandwich as the dish out making composition of body of launching box cover, pressure-bearing and the non-deformability of launching box cover are not only improved, there is light simple and easy, the simple feature of manufacture craft of structure simultaneously, and before MISSILE LAUNCHING, case lid is dished out after body is dished out and is produced without any fragment, can not produce any adverse effect to MISSILE LAUNCHING.
A kind of integral hollow composite material launching box cover of the present invention, it is characterized in that: described glass fibre layer of cloth is ladder laying structure, i.e. [(0/90) (± 45) (0/90) H (0/90) (± 45) (0/90)].
Use glass fibre layer of cloth for the beneficial effect of ladder laying structure to be: this laying structure forms quasi-isotropic composite material launching box cover structure, can evenly bear compared with large pressure limit and retention is stable, improve pressure-bearing and the non-deformability of launching box cover.
A kind of integral hollow composite material launching box cover of the present invention, is characterized in that: described V-type chamfering is 45 degree.
Use the beneficial effect of 45 degree V-type chamferings to be: lid both sides respectively have one 45 degree V-type chamfering, form double V-shaped chamfered region, 45 degree V-type chamferings can fully be filled AB glue, form the gluing connecting structure of AB with lid marginal texture same thickness, make case lid have advantages of load performance good, workable, solidify after good toughness and sealing property strong, while guaranteeing that case lid reaches the withstand voltage of setting, split rapidly in Disengagement zone simultaneously, and dish out body and framework apart are dished out, and guided missile is launched smoothly then.
A kind of integral hollow composite material launching box cover of the present invention, is characterized in that: described sandwich of layers is only positioned at the zone line of the body of dishing out (3), only there is glass fibre layer of cloth at the edge of the body of dishing out (3).
Described sandwich of layers is only positioned at the zone line of the body of dishing out, the dish out edge of body only has the beneficial effect of glass fibre layer of cloth to be: for launching box cover provides, reaction is more rapid, the more simple full composite material launching box cover of structure, does not need the opening device that provides extra; The blocked up shortcoming that but cannot ensure air-tightness of body edge thickness of avoiding dishing out, provides simple to operate simultaneously, has been easy to the process implementation method of making.
Brief description of the drawings
Fig. 1 is the integral hollow composite material launching box cover structural representation in the embodiment of the present invention 1;
Fig. 2 is the integral hollow composite material launching box cover cross-sectional view in the embodiment of the present invention 1;
Fig. 3 is the Disengagement zone structural representation in the embodiment of the present invention 1.
Fig. 4 is the integral hollow composite material launching box cover structural representation in the embodiment of the present invention 2;
Fig. 5 is the integral hollow composite material launching box cover structural representation in the embodiment of the present invention 3;
Each label title in figure: 1, framework, 2, Disengagement zone, 3, the body of dishing out, 4, integral hollow fabric, 5, lapped fiber cloth, 6, double V-shaped chamfered region, 7, epoxy glue layer.
Detailed description of the invention
Below in conjunction with accompanying drawing, by the mode of embodiment, the present invention is described in detail:
Embodiment 1
As shown in Figure 1, a kind of integral hollow composite material launching box cover, mainly designs and produces MISSILE LAUNCHING case lid taking glass fabric, integral hollow fabric and epoxide-resin glue as material of main part.Particularly, integral hollow composite material launching box cover of the present invention mainly comprises: 1, framework, and described framework quadrate, surrounding is with round-corner transition; 2, Disengagement zone, described Disengagement zone is positioned at framework and the body junction of dishing out, for glueing joint part in double V-shaped chamfered region; 3, the body of dishing out, the described body of dishing out becomes the square with round-corner transition with framework, and adopting integral hollow fabric is sandwich of layers.
Integral hollow composite material launching box cover cross-section structure as shown in Figure 2, integral hollow fabric (4) is positioned at the body center of dishing out, upper and lower both sides laminating composite layers (being glass fibre layer of cloth), adopting epoxide-resin glue is that matrix curing molding forms, the application of integral hollow fabric, the bending rigidity that has improved launching box cover, has alleviated construction weight.Dish out body edge without integral hollow fabric sandwich of layers structure, only by glass fabric and epoxide-resin glue is stacked forms, be glued together by Disengagement zone (2) and framework downwards, as shown in Figure 3.Disengagement zone adopts double V-shaped chamfering structure, and double V-shaped chamfered region (6) fill AB glue, forms the splicing district of up-down structure; Inside Disengagement zone, paving one deck lapped fiber cloth (5) is to strengthen the connectivity of dish out body and framework, and outside is coated with one deck epoxide-resin glue, has the epoxy glue layer (7) of sealing function to form one deck.This Disengagement zone version has good sealing and stability, and bearing capacity is strong, breaks through stable performance.
Embodiment 2
As shown in Figure 4, a kind of integral hollow composite material launching box cover, mainly designs and produces MISSILE LAUNCHING case lid taking glass fabric, integral hollow fabric and epoxy resin as material of main part.Particularly, integral hollow composite material launching box cover of the present invention mainly comprises: 1, framework, and described framework is circular; 2, Disengagement zone, described Disengagement zone is positioned at framework and the body junction of dishing out, for glueing joint part in double V-shaped chamfered region; 3, the body of dishing out, the described body of dishing out is circular with framework, and adopting integral hollow fabric is sandwich of layers.Its ply sequence, sandwich structure and Disengagement zone version are identical with embodiment 1.This embodiment is equipped with the launching box cover of this shape according to circular MISSILE LAUNCHING case, this structure has stressed even, does not need the outstanding stress concentration phenomenon of considering that corner occurs.Therefore, this integral hollow composite material launching box cover has better stability.
Embodiment 3
As shown in Figure 5, a kind of integral hollow composite material launching box cover, mainly designs and produces MISSILE LAUNCHING case lid taking glass fabric, integral hollow fabric and epoxy resin as material of main part.Particularly, integral hollow composite material launching box cover of the present invention mainly comprises: 1, framework, and described framework becomes hexagon, and surrounding is with round-corner transition; 2, Disengagement zone, described Disengagement zone is positioned at framework and the body junction of dishing out, for glueing joint part in double V-shaped chamfered region; 3, the body of dishing out, the described body of dishing out becomes the hexagon with round-corner transition with framework, and adopting integral hollow fabric is sandwich of layers.Its ply sequence, sandwich structure and Disengagement zone version are identical with embodiment 1.This embodiment uses in hexagon firing box structure, possesses equally good sealing, stability and bearing capacity.
Claims (5)
1. an integral hollow composite material launching box cover, comprising: framework (1) and the body of dishing out (3), and framework (1) and the body of dishing out (3) junction are called Disengagement zone (2); It is characterized in that:
The described body of dishing out (3) is by middle sandwich of layers, and the glass fibre layer of cloth of both sides is that matrix curing molding forms by epoxide-resin glue;
The described body of dishing out (3) both sides of edges respectively has a V-type chamfering, be called double V-shaped chamfered region (6), after the filling AB glue of double V-shaped chamfered region (6) with framework (1) edge-glued, and the body of dishing out (3) edge and framework (1) edge post glass fibre cloth (5) in inner side by epoxide-resin glue, seal with epoxy glue layer (7) in outside.
2. integral hollow composite material launching box cover according to claim 1, is characterized in that: described sandwich of layers is integral hollow fabric sandwich or honeycomb interlayer or corrugated plating interlayer.
3. integral hollow composite material launching box cover according to claim 1, it is characterized in that: described glass fibre layer of cloth is ladder laying structure, i.e. [(0/90) (± 45) (0/90) H (0/90) (± 45) (0/90)].
4. integral hollow composite material launching box cover according to claim 1, is characterized in that: described V-type chamfering is 45 degree.
5. integral hollow composite material launching box cover according to claim 1, is characterized in that: described sandwich of layers is only positioned at the zone line of the body of dishing out (3), only there is glass fibre layer of cloth at the edge of the body of dishing out (3).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410090565.3A CN103913099B (en) | 2014-03-12 | 2014-03-12 | Integral hollow composite material launching box cover |
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| CN201410090565.3A CN103913099B (en) | 2014-03-12 | 2014-03-12 | Integral hollow composite material launching box cover |
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| CN103913099A true CN103913099A (en) | 2014-07-09 |
| CN103913099B CN103913099B (en) | 2015-09-09 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109682255A (en) * | 2018-12-25 | 2019-04-26 | 南京航空航天大学 | Preset weak area 2.5D woven composite material Fragile cap and preparation method thereof |
| CN110749233A (en) * | 2019-10-28 | 2020-02-04 | 上海机电工程研究所 | Honeycomb adapter and method of manufacture |
| CN110953929A (en) * | 2019-11-12 | 2020-04-03 | 南京航空航天大学 | Breakable lid of carbon-fibre composite |
| CN111002646A (en) * | 2019-11-14 | 2020-04-14 | 南京航空航天大学 | Electromagnetic shielding interlayer composite material frangible cover and preparation method thereof |
| CN111256536A (en) * | 2020-02-28 | 2020-06-09 | 南京航空航天大学 | Penetration cutting wire laying reinforced plane integral breaking type frangible cover and preparation method thereof |
| CN111322909A (en) * | 2020-03-03 | 2020-06-23 | 南京航空航天大学 | Integrally-broken-type frangible cover with stepped cutting plane and preparation method thereof |
| CN111504126A (en) * | 2020-05-28 | 2020-08-07 | 北京玻钢院复合材料有限公司 | Integral separation type launching box cover and processing method thereof |
| CN115014125A (en) * | 2022-06-17 | 2022-09-06 | 北京新风航天装备有限公司 | Breakable thin film cover made of carbon fiber composite material and broken according to preset path |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109682255A (en) * | 2018-12-25 | 2019-04-26 | 南京航空航天大学 | Preset weak area 2.5D woven composite material Fragile cap and preparation method thereof |
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| CN111002646A (en) * | 2019-11-14 | 2020-04-14 | 南京航空航天大学 | Electromagnetic shielding interlayer composite material frangible cover and preparation method thereof |
| CN111256536A (en) * | 2020-02-28 | 2020-06-09 | 南京航空航天大学 | Penetration cutting wire laying reinforced plane integral breaking type frangible cover and preparation method thereof |
| CN111256536B (en) * | 2020-02-28 | 2021-06-22 | 南京航空航天大学 | Penetration cutting wire laying reinforced plane integral breaking type frangible cover and preparation method thereof |
| CN111322909A (en) * | 2020-03-03 | 2020-06-23 | 南京航空航天大学 | Integrally-broken-type frangible cover with stepped cutting plane and preparation method thereof |
| CN111504126A (en) * | 2020-05-28 | 2020-08-07 | 北京玻钢院复合材料有限公司 | Integral separation type launching box cover and processing method thereof |
| CN115014125A (en) * | 2022-06-17 | 2022-09-06 | 北京新风航天装备有限公司 | Breakable thin film cover made of carbon fiber composite material and broken according to preset path |
| CN115014125B (en) * | 2022-06-17 | 2023-07-04 | 北京新风航天装备有限公司 | Broken carbon fiber composite fragile film cover according to preset path |
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